A turbine blade tip clearance adjustable seal for an aeroengine

By introducing adjustment and locking components into the adjustable sealing device for turbine blade tip clearance, the problems of actuator ring self-locking and sealing are solved, enabling stable clearance adjustment and sealing of turbine blades under different operating conditions, thereby improving engine efficiency and safety.

CN224300954UActive Publication Date: 2026-05-29SICHUAN UNIVERSITY OF SCIENCE AND ENGINEERING
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
SICHUAN UNIVERSITY OF SCIENCE AND ENGINEERING
Filing Date
2025-06-28
Publication Date
2026-05-29

AI Technical Summary

Technical Problem

In existing active control technology for turbine tip clearance, the actuator ring cannot achieve self-locking after rotating to adjust the clearance, which easily leads to rotation, affecting turbine efficiency and safety, and also results in poor sealing.

Method used

An adjustable sealing device for the tip clearance of an aero-engine turbine blade was designed. By setting an adjustment component and a locking component between the actuating ring and the fixed ring, the self-locking and sealing performance of the tip clearance are achieved. The device includes the coordinated use of the casing body, the clearance control ring, the fixed ring, the actuating ring, the adjustment component, and the locking component.

Benefits of technology

It achieves stable adjustment of blade tip clearance under different operating conditions, improves turbine efficiency and safety, reduces fuel consumption, prevents blade tip rubbing against turbine outer ring, enhances sealing, and avoids gas leakage.

✦ Generated by Eureka AI based on patent content.

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Abstract

The utility model belongs to aero -engine turbine blade technical field provides an aero -engine turbine blade tip gap adjustable sealing device, including the casing body, the first installation groove is set up in casing body inboard wall, the fixed ring is fixedly connected with the casing body outside wall, the movable sleeve of casing body outside wall has the actuating ring, the inside of fixed ring is uniformly provided with a plurality of adjusting assembly, the inside of actuating ring is uniformly provided with a plurality of locking assembly, the utility model discloses through the cooperation of actuating ring, rocker, adjusting assembly, can adjust tip gap according to turbine front temperature change, guarantee turbine to keep reasonable tip gap under different operating conditions, improve turbine efficiency, reduce fuel consumption, the setting of locking assembly makes actuating ring realize self -locking after adjusting, avoids the change of gap due to actuating ring rotation, effectively prevents the collision of tip and turbine outer ring, improves the safety and reliability of engine work.
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Citation Information

Patent Citations

  • Active control mechanism for turbine blade tip clearance

    CN204436483U